EP1565586B1 - Produit en alliage d'aluminium aux combinaisons de proprietes ameliorees - Google Patents

Produit en alliage d'aluminium aux combinaisons de proprietes ameliorees Download PDF

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Publication number
EP1565586B1
EP1565586B1 EP03783507A EP03783507A EP1565586B1 EP 1565586 B1 EP1565586 B1 EP 1565586B1 EP 03783507 A EP03783507 A EP 03783507A EP 03783507 A EP03783507 A EP 03783507A EP 1565586 B1 EP1565586 B1 EP 1565586B1
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EP
European Patent Office
Prior art keywords
alloy
fatigue
weight
product
aircraft
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Revoked
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EP03783507A
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German (de)
English (en)
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EP1565586A4 (fr
EP1565586A2 (fr
Inventor
Gary H. Alcoa Inc. BRAY
John Alcoa Inc. LIU
Lynn Eugene Alcoa Mill Products OSWALD
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Howmet Aerospace Inc
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Alcoa Inc
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Application filed by Alcoa Inc filed Critical Alcoa Inc
Priority to EP20090003781 priority Critical patent/EP2080816A1/fr
Priority to EP10182269.0A priority patent/EP2309011A3/fr
Publication of EP1565586A2 publication Critical patent/EP1565586A2/fr
Publication of EP1565586A4 publication Critical patent/EP1565586A4/fr
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent

Definitions

  • the present invention relates to an aluminum alloy product having improved fatigue failure resistance.
  • This invention further relates to an aluminum-zinc-magnesium-copper alloy having improved fatigue failure resistance over AA 7055.
  • Aircraft manufacturers are actively engaged in producing aircraft that efficiently use high performance materials, low cost manufacturing technologies and low cost, advanced design concepts in order to lower the acquisition cost and/or increase the range and weight carrying capacity of their aircraft products.
  • Another important cost factor for airlines is the aircraft operating cost. Included in the operating cost is the cost of periodic safety inspection of aircraft components for structural damage.
  • An aircraft usually requires two types of inspections: initial inspection and periodic inspection during the operating life of the aircraft. Each type of inspection is very costly, particularly the periodic inspection because the aircraft must be taken out of service for the inspection to be performed. Inspections may require detailed visual inspection and extensive non-destructive testing of exterior and interior structures.
  • High strength structural components which excel in durability and damage tolerance are highly desired by aircraft manufacturers. Durability and damage tolerance can translate into a long interval between initial inspection and the first periodic inspection and long repeat periodic inspection intervals. Aluminum alloy structural components (such as fastened joints) that exhibit high cycle fatigue performance and fatigue crack growth resistance can translate into long inspection intervals for aircraft.
  • US Patent 6,027,582 discloses an aluminium alloy product greater 60 mm thick having 5.7-8.7% by weight Zn; 1.7-2.5% by weight Mg; 1.2-2.2% by weight Cu; 0.7-0.14% by weight Fe, 0.05-0.15% by weight Zr; less than 0.11% by weight Si; less 0.02% by weight mm and less than 0.02% by weight Cr, with Cu plus Mg less 4.1% by weight.
  • EP 1158068 discloses an aluminium alloy product comprising 4-10% by weight Zn; 124% by weight Mg; 123.5% Cu; less than 0.3% Cr; less than 0.3% Zr, less than 0.5% Si and less than 0.5% Fe.
  • US Patent 4,305,763 discloses an aluminium alloy comprises 5.9-6.9% zinc, to 2.27% magnesium, 1.9-2.5% copper, a maximum of 0.15% iron, a maximum of 0.12% silicon, a maximum of 0.06% titanium and a maximum of 0.04% chromium.
  • a principal object of this invention is the use of certain amounts of silicon in aluminium alloys having improved fatigue failure resistance.
  • an aluminium alloy product having improved fatigue failure resistance including, by weight, 7.6 to 8.4% zinc, 2.0 to 2.6% copper, 1.8 to 2.3% magnesium, 0.088 to 0.25% zirconium, the balance to 100 weight % aluminium and impurities and wherein the weight percent of iron is 0.01 to 0.09% iron for rendering the alloy substantially free of Mg 2 Si intermetallic particles
  • FIGURE 1 is a graph plotting the maximum net stress versus cycles to failure of invention alloys and comparison alloys
  • FIGURE 2 is a graph plotting maximum net stress versus cycles to failure of invention alloys and comparison alloy
  • FIGURE 3 is a schematic drawings of a test coupon
  • FIG. 4 is a graph depicting the cyclic life of joints made from invention and comparison alloys
  • FIG. 5 is a graph depicting the cyclic life of joints made from invention and comparison alloys.
  • FIG. 6 is a graph depicting the cyclic life of joints made from invention and comparison alloys.
  • ingot-derived shall mean solidified from liquid metal by known or subsequently developed casting processes rather than through powder metallurgy or similar techniques.
  • the term expressly includes, but shall not be limited to, direct chill (DC) continuous casting, electromagnetic continuous (EMC) casting and variations thereof.
  • counterpart when used to compare products made from different 7XXX alloys, shall mean a part or product, e.g. an extrusion, of generally similar section thickness or manufacturing history, or both.
  • 7055 shall mean any alloy currently or subsequently registered in this family or subgroup of 7XXX alloys.
  • substantially free means that preferably no quantity of an element is present, it being understood, however, that alloying materials, operating conditions and equipment are not always ideal such that minor amounts of undesirable contaminants or non-added elements may find their way into the invention alloy.
  • the invention provides an alloy having enhanced fatigue properties. Use of the alloy provides the opportunity for aircraft manufacturers to increase the load carrying capacity and/or increase the initial and repeat inspection intervals associated with aircraft.
  • the ranges for major alloying elements of the invention alloy, Cu, Mg, Zn and Zr are similar, as shown in Table I.
  • Table I Composition Limits of Standard 7055 Alloy and the Invention Alloy Si Fe Cu Mg Zn Zr Standard 7055 0,10 max 0.15 max 2.0 - 2.6 1.8 - 2.3 7.6 - 8.4 0.08 - 0.25
  • the important compositional differences between the invention alloy and alloy 7055 are the Si and Fe levels.
  • the invention alloy possesses surprising, significantly enhanced fatigue performance associated with Si and Fe compositional changes when compared to alloy 7055.
  • the inventors have discovered that an improvement in the invention alloy fatigue failure resistance is associated with decreasing fatigue initiation by Mg 2 Si intermetallic particles. When the Si concentration is maintained below about 0.06%, particularly below about 0.04%, the usually observed Mg 2 Si in an alloy system is absent or almost absent, thereby significantly delaying the onset of fatigue failure.
  • Mg 2 Si particle initiation is easiest, Fe-bearing particle initiation is more difficult and lattice slip is the most difficult.
  • the dominant fatigue failure mode would be lattice slip.
  • the lattice slip failure mode then requires higher fatigue stresses or longer fatigue cycles to initiate and propagate fatigue cracks than 7000 series alloys such as 7055 having higher Si and Fe contents.
  • Products made from the invention alloy, having lower Si and Fe levels than 7055 exhibit substantially better fatigue failure resistance than 7055 products of similar size and temper.
  • the invention alloy is especially well suited for critical aerospace applications, such as wing upper wing stiffened skin panels or members (typically plate and extrusion, but can be integral plate or extrusion), and other high fatigue end uses.
  • Products may be directly cast or formed into useful shapes from this alloy by any forming technique including rolling, forging and extrusion.
  • the resulting sheet, plate, extrusion, forging, rod, bar or the like may vary greatly in size and shape.
  • plate products made in accordance with this invention may have cross-sectional thicknesses ranging from about 7-5 or 8-7 mm (0.3 or 0.35 inch), up to about 37.5,50 or even 75 or more mm (1.5, 2 or even 3 or more inches). It should be further understood, however, that the invention alloy may also be made into products having cross-sectional thicknesses even smaller than about 7.5 mm (0.3 inch).
  • the alloy products of this invention are typically ingot-derived and exhibit internal structure features characteristic of ingot derivation. Once an ingot has been cast from the invention composition, it is homogenized by heating to one or more temperatures between about 460° and 493°C (860° and 920°F) after which it is worked (and sometimes machined) into a desired shape.
  • the product should then be solution heat treated by heating to one or more temperatures between about 450° or 454°C (840° or 850°F) and about 471° or 482°C (880° or 900°F) to take substantial portions, preferably all or substantially all, of the soluble zinc, magnesium and copper into solution, it being again understood that with physical processes which are not always perfect, probably every last vestige of these main alloying ingredients will not be dissolved during SHT (solutionizing).
  • the product should be rapidly cooled or quenched to complete the solution heat-treating procedure.
  • Such cooling is typically accomplished by immersion in a suitably sized tank of cold water, though water sprays and/or air chilling may be used as supplementary or substitute cooling means.
  • solution heat treat shall be meant to include quenching unless expressly stated otherwise.
  • the invention products are also amenable to age forming.
  • the age forming process involves placing the initially flat or straight products into a curved configuration by applying a load using mechanical means or vacuum bags. The subassembly of parts and tools are then placed in such equipment as autoclaves or furnaces to affect an artificial aging process. After the aging process, the product is released from the tools and some reproducible amount of springback usually occurs. The curved configuration actually compensates for the springback so that the final shape is the desired shape.
  • a typical thermal cycle for age forming involves a 10-hour soak at 150°C (302°F) followed by a 24-hour soak at 121°C (250°F). The temper derived from such a thermal cycle is also known as the T79XX temper according to the nomenclature used by the Aluminum Association.
  • mechanical properties and corrosion characteristics of the invention alloy can be mutually traded by adjusting the aging process, i.e., increased temperature and/or time within limits during artificial aging can provide alloy products with higher corrosion resistance but lower strength.
  • increased temperature and/or time within limits during artificial aging can provide alloy products with higher corrosion resistance but lower strength.
  • decreased temperature and/or time within limits can provide alloy products with higher strength but with lower corrosion resistance.
  • the invention alloy provides products suitable for use in large airplanes, such as large commercial passenger and freight aircraft. Such products, themselves, are typically large, typically several feet in length, for instance 1.5 or 3 or 75m (5 or 10 or or 50 feet) up to 30m (100 feet) or more. Yet even in these large sizes, the invention products achieve good fatigue resistance properties.
  • a particular advantage of the invention is sufficiently large size products to be suited to major structure components in aircraft, such as major wing components, wing box components, keel beam components, and the like, and subassemblies such as wing section, fuselage section, tail section (empennage).
  • Preferred embodiments of this invention possess improved fatigue failure resistance that were not previously attained with high zinc-aluminum alloys. Because such property combinations are achieved with little cost to alloy density, the invention is especially well suited for many critical aerospace applications, including upper wing assemblies and the like.
  • the S-N fatigue data for the invention and the standard 7055 product in Figure 1 were obtained for a net stress concentration factor, Kt, of 2.5 using double open hole test coupons.
  • the test coupons were 230 mm long by 25.4 mm wide by 3.17 mm thick and had two 4.75 mm in diameter holes, spaced 25.4 mm apart along the coupon length.
  • the test frequency was 25 Hz and the test was performed in ambient laboratory air.
  • the invention showed significant improvements in fatigue life with respect to the standard 7055 product.
  • the invention alloy had a lifetime (based on the log average of all specimens tested at that stress) of 355485 cycles compared to 47692 for the standard 7055 alloy. This represents a seven times (645% improvement) improvement in life which could be utilized to delay the initial inspection interval in an aircraft structure.
  • the invention alloy exhibits a significant improvement in the stress level corresponding to a given lifetime.
  • a lifetime of 100000 cycles corresponds to a maximum net section stress of 224 MPa compared to 190 MPa in the standard 7055 alloy. This represents an improvement of 18% which could be utilized by an aircraft manufacturer to increase design stress of an aircraft, thereby saving weight, while maintaining the same inspection interval for the aircraft.
  • the invention alloy exhibited significant improvements in fatigue life with respect to the comparison 7055 products.
  • the invention alloy had a mean lifetime (based on the Box-Cox fit) of 415147 cycles representing a 2.4 times (144% improvement) improvement in life compared to the standard 7055 alloy which had a mean lifetime of 170379 cycles.
  • the maximum net section stress at a lifetime of 100000 cycles was 240 MPa in the invention alloy compared to 220 in the standard 7055 alloy, an improvement of 9%. While this improvement is not as great as that previously observed in Example 1, the magnitude of the improvement is expected to vary with differences in specimen design, specimen fabrication procedures and testing conditions, as previously discussed.
  • the first set of low-load transfer joints fabricated from Invention Lot V and Comparison Lot Y consisted of two dogbone details having a width in the reduced section of 25.4 mm and a thickness of 8 mm.
  • the length of the reduced section was 70 mm while the overall length of the specimen (i.e., including grip ends) was 455 mm.
  • the dogbone details Prior to assembly, the dogbone details were chromic acid anodized and primed with zinc chromate primer.
  • the two fastener holes were drilled and reamed to a final diameter of 6.16 mm (0.2465 inch).
  • the hole pitch was 25.4 mm.
  • One side of one hole in each detail was countersunk using a 109° countersink tool to accommodate the fastener head.
  • Aerospace quality fuel tank sealant was spread on the faying surfaces of the dogbone details. The two details were then joined with two 6.25 mm (0.250-inch) diameter interference fit fasteners having a nominal interference of 0.0625 mm (0.0025 inch).
  • the fasteners were Ti pin HST755KN and steel nut NSA 5474. The nuts were torqued to 3.7-4.3 Nm (60-70 in-lbs).
  • Five specimens of the invention alloy and five of the standard 7055 alloy were tested at a mean stress of -60 MPa and an alternating stress of + 155 MPa.
  • the test environment was lab air having a relative humidity of 35 to 52% and the test frequency was 18 Hz. The results of these tests are given in Figure 4 .
  • the line between the results from the two alloys connects the mean of the invention alloy and the comparison alloy.
  • the invention alloy had an average lifetime of 211141 cycles compared to 134176 for the standard 7055 alloy, an increase in life of about 1.5 times or an improvement of 57%.
  • the second set of low-load transfer joints fabricated from Invention Lot W and Comparison Lot Z consisted of two dogbone details having a width in the reduced section of 31.7 mm and a thickness of 6.35 mm.
  • the length of the reduced section was 76.2 mm while the overall length of the specimen (i.e., including grip ends) was 355 mm.
  • the fastener hole pitch was 31.75 mm.
  • the remainder of the fabrication and assembly details was essentially the same as Set 1 except the fasteners.
  • the fasteners were steel pin HL19B and aluminum collar HL70. Seven specimens of the invention alloy and seven of the standard 7055 alloy were tested at mean stress of +102.4 MPa and an alternating stress of ⁇ 83.8 MPa.
  • the test environment was high humidity air having a relative humidity greater than 90% and the test frequency was 11 Hz.
  • the results of these tests are given in Figure 5 .
  • the invention alloy had an average lifetime of 551701 cycles compared to 210824 for the standard 7055 alloy, an increase in life of 2.6 times or an improvement of 162%.
  • the third set of low-load transfer joints fabricated from Invention Lot X and Comparison Lot Z were of the same dimensions as the second set and their fabrication and their fabrication and assembly were essentially the same as Sets 1 and 2 except for the fasteners.
  • the fasteners were Ti pin HST755 and aluminum nut KFN 587.
  • Four specimens of the invention alloy and six of the standard 7055 alloy were tested at mean stress of -60 MPa and an alternating stress of ⁇ 155 MPa.
  • the test environment was high humidity air having a relative humidity greater than 90% and the test frequency was 18 Hz. The results of these tests are given in Figure 6 .
  • the invention alloy had an average lifetime of 445866 cycles compared to 217572 for the standard 7055 alloy, an increase in life of about 2 times or an improvement of 105%.

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Claims (6)

  1. Utilisation de 0,01 à moins de 0,04 % de silicium dans un produit en alliage d'aluminium ayant une résistance à la rupture par fatigue améliorée comprenant, en % poids, 7,6 à 8,4 % de zinc, 2,0 à 2,6 % de cuivre, 1,8 à 2,3 % de magnésium, 0,088 à 0,25 % de zirconium, le reste de 100 % poids d'aluminium et d'impuretés, et dans laquelle le pourcentage en poids de fer est maintenu à entre 0,01 et 0,09 %, pour rendre l'alliage essentiellement pur de particules intermétalliques Mg2Si.
  2. L'utilisation de la revendication 1, dans laquelle ledit produit est une plaque, une feuille, une extrusion, une pièce forgée ou une pièce moulée.
  3. L'utilisation de la revendication 2, qui est une plaque adaptée pour une utilisation comme membre d'aile supérieure.
  4. L'utilisation de la revendication 1, qui a été soumise à un traitement thermique de mise en solution, à un traitement pour l'élimination des contraintes par l'intermédiaire d'un écrouissage, et à un vieillissement artificiel.
  5. L'utilisation de la revendication 1, dans laquelle le produit en alliage amélioré est une extrusion en alliage ayant une coupe transversale comprenant une épaisseur inférieure à 3 pouces.
  6. L'utilisation de la revendication 5, dans laquelle l'extrusion en alliage a une meilleure résistance à la rupture par fatigue qu'un produit 7055 de taille, de forme, d'épaisseur et de trempe similaires.
EP03783507A 2002-11-15 2003-11-17 Produit en alliage d'aluminium aux combinaisons de proprietes ameliorees Revoked EP1565586B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20090003781 EP2080816A1 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés
EP10182269.0A EP2309011A3 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US42659702P 2002-11-15 2002-11-15
US426597P 2002-11-15
PCT/US2003/036490 WO2004046403A2 (fr) 2002-11-15 2003-11-17 Produit en alliage d'aluminium aux combinaisons de proprietes ameliorees

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EP20090003781 Division EP2080816A1 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés

Publications (3)

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EP1565586A2 EP1565586A2 (fr) 2005-08-24
EP1565586A4 EP1565586A4 (fr) 2006-08-02
EP1565586B1 true EP1565586B1 (fr) 2009-06-10

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EP20090003781 Withdrawn EP2080816A1 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés
EP10182269.0A Withdrawn EP2309011A3 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés
EP03783507A Revoked EP1565586B1 (fr) 2002-11-15 2003-11-17 Produit en alliage d'aluminium aux combinaisons de proprietes ameliorees

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EP20090003781 Withdrawn EP2080816A1 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés
EP10182269.0A Withdrawn EP2309011A3 (fr) 2002-11-15 2003-11-17 Produit d'alliage en aluminium doté de combinaisons améliorées de propriétés

Country Status (9)

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US (1) US7097719B2 (fr)
EP (3) EP2080816A1 (fr)
AT (1) ATE433503T1 (fr)
AU (1) AU2003290922A1 (fr)
BR (1) BRPI0315625B8 (fr)
CA (1) CA2506393C (fr)
DE (1) DE60327941D1 (fr)
ES (1) ES2329674T3 (fr)
WO (1) WO2004046403A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2823075A4 (fr) * 2012-03-07 2016-01-27 Alcoa Inc Alliages d'aluminium de la série 7xxx améliorés et leurs procédés de production
CN108754258A (zh) * 2018-06-26 2018-11-06 安徽沪源铝业有限公司 一种7055铝合金及其时效工艺

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DE112004003147B4 (de) 2003-04-10 2022-11-17 Novelis Koblenz Gmbh Al-Zn-Mg-Cu-Legierung
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US7883591B2 (en) * 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
DE502005001724D1 (de) * 2005-01-19 2007-11-29 Fuchs Kg Otto Abschreckunempfindliche Aluminiumlegierung sowie Verfahren zum Herstellen eines Halbzeuges aus dieser Legierung
US20060213591A1 (en) 2005-03-24 2006-09-28 Brooks Charles E High strength aluminum alloys and process for making the same
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8608876B2 (en) * 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
WO2008003504A2 (fr) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Produits en alliage d'aluminium série aa7000, et procédé de fabrication correspondant
US8673209B2 (en) * 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8840737B2 (en) * 2007-05-14 2014-09-23 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8333853B2 (en) * 2009-01-16 2012-12-18 Alcoa Inc. Aging of aluminum alloys for improved combination of fatigue performance and strength
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
US9587298B2 (en) 2013-02-19 2017-03-07 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
RU2556849C1 (ru) * 2014-04-14 2015-07-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Высокопрочный сплав на основе алюминия и изделие, выполненное из него
ES2929839T3 (es) 2018-06-12 2022-12-02 Novelis Koblenz Gmbh Método de fabricación de un producto en placa de aleación de aluminio de la serie 7xxx que tiene una resistencia mejorada al fallo por fatiga

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US4305763A (en) * 1978-09-29 1981-12-15 The Boeing Company Method of producing an aluminum alloy product
US5108520A (en) 1980-02-27 1992-04-28 Aluminum Company Of America Heat treatment of precipitation hardening alloys
US5221377A (en) 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
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US7135077B2 (en) * 2000-05-24 2006-11-14 Pechiney Rhenalu Thick products made of heat-treatable aluminum alloy with improved toughness and process for manufacturing these products
IL156386A0 (en) * 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2823075A4 (fr) * 2012-03-07 2016-01-27 Alcoa Inc Alliages d'aluminium de la série 7xxx améliorés et leurs procédés de production
CN108754258A (zh) * 2018-06-26 2018-11-06 安徽沪源铝业有限公司 一种7055铝合金及其时效工艺

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Publication number Publication date
ATE433503T1 (de) 2009-06-15
CA2506393A1 (fr) 2004-06-03
EP2309011A3 (fr) 2013-05-08
EP2309011A2 (fr) 2011-04-13
EP1565586A4 (fr) 2006-08-02
EP1565586A2 (fr) 2005-08-24
US7097719B2 (en) 2006-08-29
US20040136862A1 (en) 2004-07-15
WO2004046403A2 (fr) 2004-06-03
BR0315625A (pt) 2005-08-23
CA2506393C (fr) 2009-10-27
AU2003290922A8 (en) 2004-06-15
DE60327941D1 (de) 2009-07-23
EP2080816A1 (fr) 2009-07-22
BRPI0315625B8 (pt) 2022-11-08
BRPI0315625B1 (pt) 2013-06-04
WO2004046403A3 (fr) 2004-07-01
ES2329674T3 (es) 2009-11-30
AU2003290922A1 (en) 2004-06-15

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